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Title: Regeneratively cooled transition duct with transversely buffered impingement nozzles

Patent ·
OSTI ID:1178277
; ;

A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to form impingement cooling jets (70) emanating from dimples (82) in the flow sleeve effective to predominately cool the duct in an impingement cooling zone (60), and wherein the flow sleeve defines a convection cooling zone (64) effective to cool the duct solely via a cross-flow (76), the cross-flow comprising cooling fluid (72) exhausting from the impingement cooling zone. In the impingement cooling zone an undimpled portion (84) of the flow sleeve tapers away from the duct as the undimpled portion nears the convection cooling zone. The flow sleeve is configured to effect a greater velocity of the cross-flow in the convection cooling zone than in the impingement cooling zone.

Research Organization:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42644
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Number(s):
9,010,125
Application Number:
13/956,405
OSTI ID:
1178277
Resource Relation:
Patent File Date: 2013 Aug 01
Country of Publication:
United States
Language:
English

References (21)

Gas turbine combustion apparatus patent October 1989
Breach-cooled structure patent April 1990
Uniform cooling film replenishment thermal liner assembly patent November 1993
Gas turbine airfoil patent October 1994
Gas turbine combustion chamber with impingement cooling tubes patent February 1995
Turbine cooling blade having inner hollow structure with improved cooling patent July 1996
Baffle-cooled wall part patent December 1996
Thermal spreading combustor liner patent May 1998
Thermal spreading combustion liner patent October 1999
Cooling for double-wall structures patent December 1999
Dimpled impingement baffle patent May 2001
Turbine blade wall section cooled by an impact flow patent August 2002
Combustor liner cooling thimbles and related method patent November 2002
Tangential flow baffle patent April 2003
Arrangement for using a plate shaped element with through-openings for cooling a component patent September 2003
Method and apparatus for cooling combustor liner and transition piece of a gas turbine patent February 2009
Combustion transition duct providing stage 1 tangential turning for turbine engines patent May 2010
Wavy CMC wall hybrid ceramic apparatus patent March 2011
Method of fabricating a nearwall nozzle impingement cooled component for an internal combustion engine patent-application November 2012
Method of forming a multi-panel outer wall of a component for use in a gas turbine engine patent-application November 2012
Ducting Arrangement For Cooling A Gas Turbine Structure patent-application April 2014

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